Wind-tunnel investigation of a flush airdata system at Mach numbers from 0.7 to 1.4
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Wind-tunnel investigation of a flush airdata system at Mach numbers from 0.7 to 1.4

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Published by National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, For sale by the National Technical Information Service in Edwards, Calif, Springfield, VA .
Written in English

Subjects:

  • Aeronautical instruments.,
  • Air data systems.,
  • Algorithms.,
  • Flight tests.,
  • Flushing.,
  • Wind tunnel tests.,
  • Wind tunnels.

Book details:

Edition Notes

StatementTerry J. Larson, Timothy R. Moes, Paul M. Siemers III.
SeriesNASA technical memorandum -- 101697.
ContributionsMoes, Timothy R., Siemers, Paul M., Dryden Flight Research Facility.
The Physical Object
FormatMicroform
Paginationiii, 31 p.
Number of Pages31
ID Numbers
Open LibraryOL18263198M

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These tests, which were published, are part of a NASA program to assess accuracies of FADS for use on aircraft. The test program also provides data to validate algorithms for the shuttle entry airdata system developed at the NASA Langley Research Center. The wind-tunnel test Mach numbers were , , , , and Get this from a library! Wind-tunnel investigation of a flush airdata system at Mach numbers from to [Terry J Larson; Timothy R Moes; Paul M Siemers; Dryden Flight Research Facility.]. Aug 20,  · Evaluation of the Cross Wind Velocity Through Pressure Measurements on Train Surface. Authors; T.J., Moes, T.R., Siemers III, P.M.: Wind tunnel investigation of a flush airdata system at Mach numbers from to Schito P., Tomasini G. () Evaluation of the Cross Wind Velocity Through Pressure Measurements on Train Surface. Cited by: 1. Jul 25,  · Abstract. Flush air data sensing (FADS) systems have been successfully tested on the nose tip of large manned/unmanned air vehicles. In this paper we investigate the application of a FADS system on the wing leading edge of a micro (unmanned) air vehicle (MAV) flown at speed as low as Mach Cited by:

Trade-off design of measurement tap configuration and solving model for a flush air data sensing system P.M. SiemersWind-Tunnel Investigation of a Flush Airdata System at Mach Numbers from to ; NASA TMAuthor: YanBin Liu, DiBo Xiao. Wind Tunnel Tests at Mach Numbers up to on a Model with Scale Wings and Nacelles of a Twin-Engined Supersonic Aircraft (Bristol ) bY E. P. Sutton, P. G. Hutton and L. C. Squire numbers betvcen and and between and at a Reynolds nuniber. A novel numerical model which calculates the air data for flush airdata system was developed based on the Kriging interpolation. This method constructs the transformation matrix between the inputs i.e. the pressure measured by the sensor and the outputs i.e. angle of attack, angle of slide and Mach number; hence the required air data can be directly computed without pandudesign.com by: 1. For this reason, this method is used with combination of other means, for example, the Mach number is obtained by the inertial navigation system first, and then the angle of attack and the sideslip angle are obtained using the look-up method. Siemers, P.M. Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers from to Cited by: 1.

WIND-TUNNEL INVESTIGATION OF A FLUSH AIRDATA SYSTEM AT MACH NUMBERS FROM TO , Technical Memorandum Authors: Terry J. Larson, Timothy R. Moes and Paul M. Siemers, III Report Number: NASA-TM Performing Organization: . Development and Evaluation of Neural Network Models for Cost Reduction in Unmanned Air Vehicles. Siemers III, “Wind tunnel investigation of a flush airdata system at Mach numbers from to ”, NASA TM,Author: Ihab Samy Abou Rayan. Tests of humidity effects on flow in a wind tunnel at Mach numbers between and 4 by R.J. Monaghan, M.A. SUMMARY Static and pitot pressure distributions were measured in the -working section of a 5 in. x 5 in. supersonic wind tunnel at nominal Mach numbers of , and 4, over ranges of absolute humidity at the inlet from. Flight and Wind-Tunnel Calibrations of a Flush Airdata Sensor at High Angles of Attack and Sideslip and at Supersonic Mach Numbers Timothy R. Moes, Stephen A. Whitmore, and Frank L. Jordan, Jr. (NASA-TM) FLIGHT AND WIND-TUNNEL CALIBRATIONS OF A FLUSH AIRDATA SENSOR AT HIGH ANGLES OF ATTACK AND SIDESLIP AND AT SUPERSONIC MACH NUMBERS.